US6333118B1 - Heat barrier composition, a mechanical superalloy article provided with a ceramic coating having such a composition, and a method of making the ceramic coating - Google Patents
Heat barrier composition, a mechanical superalloy article provided with a ceramic coating having such a composition, and a method of making the ceramic coating Download PDFInfo
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- US6333118B1 US6333118B1 US09/659,818 US65981800A US6333118B1 US 6333118 B1 US6333118 B1 US 6333118B1 US 65981800 A US65981800 A US 65981800A US 6333118 B1 US6333118 B1 US 6333118B1
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- C—CHEMISTRY; METALLURGY
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- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/48—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on zirconium or hafnium oxides, zirconates, zircon or hafnates
- C04B35/486—Fine ceramics
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- C—CHEMISTRY; METALLURGY
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- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
- C04B2235/3225—Yttrium oxide or oxide-forming salts thereof
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
- C04B2235/9607—Thermal properties, e.g. thermal expansion coefficient
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12611—Oxide-containing component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12611—Oxide-containing component
- Y10T428/12618—Plural oxides
Definitions
- the invention relates to a low thermal conductivity heat barrier composition, a mechanical superalloy article provided with a protective heat barrier ceramic coating having such a composition, and a method of making the ceramic coating.
- An alternative to changing the family of materials is to deposit a heat-insulating ceramic coating, called a heat barrier, on the superalloy articles.
- This ceramic coating enables a cooled article to have, during continuous operation, a thermal gradient across the ceramic which is possibly more than 200° C.
- the working temperature of the metal below is reduced in proportion, with considerable effect on the volume of cooling air required, the working life of the article, and the specific fuel consumption of the engine.
- the ceramic coating may be deposited on the article to be coated by various processes, most of which belong to two different categories, namely sprayed coatings and physical vapour phase deposited coatings.
- Other deposition processes of the plasma assisted chemical vapour phase deposition (CVD) type can also be used.
- a zirconia based oxide is deposited by a plasma spraying technique.
- the coating consists of a stack of melted ceramic droplets which are then quenched, flattened and stacked to form an incompletely densified deposit between 50 ⁇ m and 1 mm thick.
- One of the characteristics of this kind of coating is a high intrinsic roughness (the roughness Ra being typically between 5 and 35 ⁇ m).
- the commonest kind of degradation associated with this coating in use is the slow propagation of a crack in the ceramic parallel to the ceramic/metal interface.
- the problem is rather different in the case of coatings deposited by physical vapour phase deposition.
- a deposition of this kind can be made by evaporation under electron bombardment.
- the main characteristic is that the coating consists of an assembly of very fine columns, typically between 0.2 and 10 ⁇ m, which extend substantially perpendicularly to the surface to be coated.
- the thickness of such a coating can be between 20 and 600 ⁇ m.
- Such an assembly has the useful property of faithfully reproducing the surface texture of the substrate covered. In particular, in the case of turbine blades this enables a final roughness of considerably less than 1 ⁇ m to be obtained, which is very advantageous for the aerodynamic properties of the blade.
- Chemical vapour phase deposition techniques produce coatings whose morphology is columnar and substantially equivalent to the morphology of physical vapour phase deposits. In both these techniques the formation of oxide results from a molecular reaction between metallic atoms or ions and oxygen.
- the heat barrier coatings consist of a mixture of oxides, usually having a zirconia base. This oxide is a useful compromise between a material of fairly low thermal conductivity and a material of relatively high coefficient of expansion near that of the nickel or cobalt based alloys on which it is required to deposit the coating.
- One of the ceramic compositions which has proved very satisfactory is zirconia completely or partly stabilised by an oxide such as, for example, yttrium oxide: ZrO 2 +6 to 8 Wt. % of Y 2 O 3 .
- the yttrium oxide serves to stabilise the cubic allotropic variety C and/or the non-transformable tetragonal variety t′ of the zirconia and thus to prevent martensitic phase transitions in response to excursions between ambient temperature and the high working temperature of the article.
- the main requirement of a heat barrier coating is that it should slow down heat exchanges between an external environment of hot gases and the coated metal article, which is nearly always cooled by a forced flow of cold gases. Heat exchange between the ceramic coating and the metal below it can be by conduction and, to a lesser extent, by radiation.
- the thermal conductivity of an oxide is of course the sum of a phonic contribution which varies as a function of 1/T and of a radiant contribution which varies as a function of T 3 . In the case of partly or completely stabilised zirconias it is found that the radiant contribution is substantial beyond 500° C. in a monocrystal (thermal conductivity increases rapidly with temperature) but is negligible up to 1200° C.
- heat barrier coatings arc porous ceramic layers and the thermal conductivity of the coating is that of a heterogeneous assembly of two heat-conducting media, namely the ceramic material itself of intrinsic conductivity ⁇ intr , and the pores or microcracks of the coating whose conductivity is close to that of the gas filling them under operating conditions.
- the effective conductivity ⁇ actual of the coating is between ⁇ intr and the conductivity of air ⁇ air . It can in fact be stated that ⁇ actual is a complex function of ⁇ intr and ⁇ air and the morphology of the coating.
- a first solution to the problem of obtaining a low thermal conductivity coating is to use a ceramic of conventional ceramic composition, such as zirconia partly stabilised by 6 to 8 wt. % of yttrium oxide, and to modify the morphology of the coating—i.e., the proporation, distribution and orientation of the pores and microcracks of the coating, or the arrangement of the material in the form of columns or strata—so as to reduce ⁇ actual .
- This result can be achieved by modifying the coating deposition parameters.
- a second solution is to try to reduce ⁇ intr directly by modifying the chemical composition of the coating, without altering its morphology and while conserving the other properties of the coating.
- the introduction of yttrium into zirconia reduces its thermal conductivity by creating gaps in the lattice due to the zirconium ions having a different valency from the yttrium ions.
- the introduction of spot defects into the lattice which act as phonon retrodiffusion centres helps to reduce thermal conductivity, and this is the solution which is used in the present invention.
- a first oxide serving to stabilise the tetragonal or cubic form of the zirconia this oxide possibly being yttrium oxide, calcium oxide, magnesium oxide, indium oxide, scandium oxide, or ytterbium oxide;
- a second oxide serving to reduce phonic thermal conductivity and absorbing radiant energy in the waveband between 0.3 and 5 ⁇ m to reduce heat conductivity due to photons.
- the ceramic zirconia-based layer contains three additional oxides, namely:
- a first oxide serving to stabilise the tetragonal or cubic form of the zirconia this oxide possibly being yttrium oxide, calcium oxide, magnesium oxide, indium oxide, scandium oxide, or ytterbium oxide;
- a third oxide which absorbs the radiant energy in the waveband between 0.3 and 5 ⁇ m to reduce thermal conductivity due to photons.
- compositions proposed in this document are complex and expensive.
- the invention provides a low thermal conductivity heat barrier composition composed of a zirconia base and a dysprosium oxide having the dual function of stabilishing the zirconia and reducing the thermal conductivity of the zirconia due to phonons. More particularly the dysprosium oxide serves to stabilise the zirconia and reduce the intrinsic conductivity of the ceramic by the introduction of spot defects in the lattice while preserving its other main characteristics such as, for example, the nature of the phases, the coefficient of expansion, and the refractory properties.
- the proportion of the dysprosium ion in the composition is between 2 and 30 atomic wt. %.
- the zirconia may also contain between 0 and 30 mol. % of an oxide containing a quadrivalent metallic ion of greater mass than the zirconium ion, the quadrivalent metallic ion oxide preferably being hafnium dioxide, cerium dioxide, uranium dioxide, or a mixture of these oxides.
- composition in accordance with the invention is particularly useful for forming a ceramic heat barrier coating on a mechanical superalloy article.
- the ceramic coating is deposited on a bonding underlayer consisting of an alloy adapted to form a protective alumina layer.
- This alloy may be, for example, of the MCrAlY type, wherein M is a metal selected from nickel, cobalt, iron, and mixtures of these metals.
- the alloy may also be a nickel aluminide possibly containing one or more metals selected from chromium and the precious metals such as platinum, palladium, ruthenium, iridium, osmium and rhodium.
- the invention also provides a method of making a heat barrier coating on a superalloy substrate comprising the steps of:
- a ceramic coating comprising zirconia, a dysprosium oxide to stabilise the zirconia and reduce the phonic thermal conductivity of the zirconia, and, optionally, from 0 to 30 mol. % of an oxide selected from the group consisting of hafnium dioxide, cerium dioxide, uranium dioxide, and mixtures thereof.
- FIG. 1 is a schematic section, to an enlarged scale, showing a mechanical superalloy article comprising a ceramic heat barrier coating formed in accordance with the invention.
- FIG. 2 is a graph showing the comparative values of thermal conductivity obtained at different temperatures for a heat barrier coating formed by a ceramic having a composition in accordance with the invention and for a heat barrier coating formed by a conventional ceramic.
- the mechanical article shown in FIG. 1 comprises a heat barrier coating 1 deposited on a substrate 2 made of a superalloy such as a nickel and/or cobalt based superalloy.
- the coating 1 comprises a metallic underlayer 3 deposited on the substrate 2 by a process which is known in the art, and a ceramic layer 4 of novel composition in accordance with the invention deposited on the underlayer 3 .
- the ceramic 4 consists of a zirconia base and a dysprosium oxide for stabilising the zirconia and surprisingly having the advantage of reducing the thermal conductivity of the ceramic to a much greater extent than the other conventionally used oxides.
- the ceramic may also contain an additional metal oxide comprising a quadrivalent metallic ion having an atomic mass greater than the atomic mass of zirconium ions.
- the quadrivalent metallic ion may be cerium, hafnium, or uranium.
- dysprosium oxide in its dual function as a zirconia stabiliser and an oxide appreciably reducing the conductivity of zirconia by reducing the conductivity due to phonons in the material, the following test was made.
- Hastelloy X alloy is used as a substrate, and is coated with a MCrAlY type metallic underlayer by a known process.
- a ceramic coating in accordance with the invention is then electron beam vapour deposited on the underlayer.
- the composition of the ceramic coating is as follows:
- the coated article is given a stabilishing heat treatment in vacuo at 1080° C. for 2 hours.
- the columnar structure ceramic coating prepared by the process used has a density of 4800 kg/m 3 and a thickness of 190 ⁇ m. X-ray diffraction examination of the crystallographic structure of the coating shows that it consists entirely of the cubic phase, which remains stable after 100 hours exposure to 1250° C.
- the thermal conductivity of the ceramic coating was determined as in Example 1, but at temperatures varying between 20° C. and 1100° C. In this case no correction was made for coating porosity.
- the thermal conductivity values of this ceramic were compared with those obtained from a conventional ceramic having the composition ZrO 2 +8 wt. % Y 2 O 3 and prepared by the same process in order to assess the conductivity reduction provided by the invention. A check was made to ensure that both ceramics had the same microstructure to make sure that the difference between the thermal conductivities of the two materials arise from their different compositions and not from any differences in microstructure.
- the comparative thermal conductivity values obtained at various temperatures for a coating comprising a ceramic having a composition in accordance with the invention and for a coating comprising a conventional ceramic are shown in FIG. 2 .
- the measured thermal conductivity of the novel ceramic is 1.08 W/m.K at 20° C. whereas the thermal conductivity of the conventional ceramic is 2.19 W/m.K.
- the novel ceramic therefore halves the thermal conductivity at 20° C.
- FIG. 2 therefore shows that the thermal conductivity of the novel ceramic is appreciably less than that of the conventional ceramic at all temperatures.
- a ceramic coating is plasma sprayed on to a Hastelloy X article which has previously been coated with a MCrAlY type metallic underlayer.
- the composition of the ceramic coating is as follows:
- the raw sprayed coating is given a heat treatment in air at 1100° C. for 10 hours in order to stabilise the ceramic in a state representative of its use in operation (this treatment having the special feature of restoring the stoichiometry of the oxides present in the ceramic).
- this treatment having the special feature of restoring the stoichiometry of the oxides present in the ceramic.
- the coating in accordance with the invention has a porosity level very close to that conventionally measured for a ceramic having the composition ZrO 2 +8 wt. % Y 2 O 3 prepared by the same process, namely approximately 8.5% porosity.
- the measured thermal conductivity of the ZrO 2 +11.2 wt. % Dy 2 O 3 coating is 0.81 W/m.K. at 1100° C., compared to 1.19 W/m.K. for the conventional ceramic coating.
- the novel ceramic composition described in this example therefore achieves a more than 30% improvement in the insulation provided by the ceramic.
- the bonding underlayer may consist of some other alloy such as, for example, plain nickel aluminide or nickel aluminide modified by metals such as chromium, platinum, palladium, ruthenium, iridium, osmium and rhodium.
- the zirconia may also contain between 0 and 30 mol. % of an oxide containing a quadrivalent metallic ion of greater atomic mass than the zirconium ions.
- the oxide may be hafnium dioxide or cerium dioxide.
- the coated article may be made of a superalloy other than Hastelloy X.
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- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
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- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Compositions Of Oxide Ceramics (AREA)
Abstract
Description
Composition | Conductivity in W/m.K | ||
ZrO2 + 4 mol. % Y2O3 | 2.8 | ||
ZrO2 + 4 mol. % Dy2O3 | 2.4 | ||
ZrO3 + l2 mol. % Dy2O3 | 1.7 | ||
ZrO2 | base | ||
Dy2O3 | 29.2 wt. % | ||
ZrO2 | base | ||
Dy2O3 | 11.2 wt. % | ||
Claims (19)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR9911565A FR2798654B1 (en) | 1999-09-16 | 1999-09-16 | LOW THERMAL CONDUCTIVITY THERMAL BARRIER COMPOSITION, SUPERALLOY MECHANICAL PART PROTECTED BY A CERAMIC COATING HAVING SUCH A COMPOSITION, AND METHOD FOR PRODUCING THE CERAMIC COATING |
FR9911565 | 1999-09-16 |
Publications (1)
Publication Number | Publication Date |
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US6333118B1 true US6333118B1 (en) | 2001-12-25 |
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Application Number | Title | Priority Date | Filing Date |
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US09/659,818 Expired - Lifetime US6333118B1 (en) | 1999-09-16 | 2000-09-11 | Heat barrier composition, a mechanical superalloy article provided with a ceramic coating having such a composition, and a method of making the ceramic coating |
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US (1) | US6333118B1 (en) |
EP (1) | EP1085109B1 (en) |
JP (1) | JP2001151571A (en) |
AT (1) | ATE422565T1 (en) |
CA (1) | CA2318612C (en) |
DE (1) | DE60041526D1 (en) |
ES (1) | ES2317825T3 (en) |
FR (1) | FR2798654B1 (en) |
Cited By (38)
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US20040038085A1 (en) * | 2002-08-21 | 2004-02-26 | Litton David A. | Thermal barrier coatings with low thermal conductivity |
WO2004029330A1 (en) * | 2002-09-25 | 2004-04-08 | Volvo Aero Corporation | A thermal barrier coating and a method of applying such a coating |
US20040115410A1 (en) * | 2002-12-12 | 2004-06-17 | Nagaraj Bangalore Aswatha | Thermal barrier coating protected by tantalum oxide and method for preparing same |
US20040126599A1 (en) * | 2002-09-25 | 2004-07-01 | Volvo Aero Corporation | Thermal barrier coating and a method of applying such a coating |
US20040126486A1 (en) * | 2001-06-13 | 2004-07-01 | Taiji Torigoe | Method of repairing a Ni-base alloy part |
US20040156724A1 (en) * | 2001-06-15 | 2004-08-12 | Taiji Torigoe | Thermal barrier coating material method of production thereof, gas turbine member using the thermal barrier coating material, and gas turbine |
US20040175597A1 (en) * | 2002-08-21 | 2004-09-09 | Litton David A. | Turbine components with thermal barrier coatings |
US20040190351A1 (en) * | 2003-03-24 | 2004-09-30 | Kabushiki Kaisha Toshiba | Leak immune semiconductor memory |
US6858334B1 (en) | 2003-12-30 | 2005-02-22 | General Electric Company | Ceramic compositions for low conductivity thermal barrier coatings |
US6869703B1 (en) | 2003-12-30 | 2005-03-22 | General Electric Company | Thermal barrier coatings with improved impact and erosion resistance |
US6875529B1 (en) | 2003-12-30 | 2005-04-05 | General Electric Company | Thermal barrier coatings with protective outer layer for improved impact and erosion resistance |
US6887595B1 (en) | 2003-12-30 | 2005-05-03 | General Electric Company | Thermal barrier coatings having lower layer for improved adherence to bond coat |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3525597A (en) | 1968-11-13 | 1970-08-25 | Us Air Force | Transparent zirconia and process for making same |
EP0354573A2 (en) | 1988-08-10 | 1990-02-14 | W.R. Grace & Co.-Conn. | Stabilized zirconia |
EP0812931A1 (en) | 1996-06-13 | 1997-12-17 | Tosoh Corporation | Vapor deposition material |
EP0825271A1 (en) | 1996-08-16 | 1998-02-25 | ROLLS-ROYCE plc | A metallic article having a thermal barrier coating and a method of application thereof |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0621040B2 (en) * | 1985-07-23 | 1994-03-23 | 川崎製鉄株式会社 | Method for producing high-purity zirconia powder |
JPH1161438A (en) * | 1997-08-27 | 1999-03-05 | Toshiba Corp | Heat shielding coating member and its production |
-
1999
- 1999-09-16 FR FR9911565A patent/FR2798654B1/en not_active Expired - Lifetime
-
2000
- 2000-09-06 CA CA2318612A patent/CA2318612C/en not_active Expired - Lifetime
- 2000-09-11 US US09/659,818 patent/US6333118B1/en not_active Expired - Lifetime
- 2000-09-12 JP JP2000276378A patent/JP2001151571A/en active Pending
- 2000-09-14 ES ES00402538T patent/ES2317825T3/en not_active Expired - Lifetime
- 2000-09-14 DE DE60041526T patent/DE60041526D1/en not_active Expired - Lifetime
- 2000-09-14 AT AT00402538T patent/ATE422565T1/en not_active IP Right Cessation
- 2000-09-14 EP EP00402538A patent/EP1085109B1/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3525597A (en) | 1968-11-13 | 1970-08-25 | Us Air Force | Transparent zirconia and process for making same |
EP0354573A2 (en) | 1988-08-10 | 1990-02-14 | W.R. Grace & Co.-Conn. | Stabilized zirconia |
EP0812931A1 (en) | 1996-06-13 | 1997-12-17 | Tosoh Corporation | Vapor deposition material |
EP0825271A1 (en) | 1996-08-16 | 1998-02-25 | ROLLS-ROYCE plc | A metallic article having a thermal barrier coating and a method of application thereof |
US6025078A (en) * | 1996-08-16 | 2000-02-15 | Rolls-Royce Plc | Metallic article having a thermal barrier coating and a method of application thereof |
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Also Published As
Publication number | Publication date |
---|---|
EP1085109B1 (en) | 2009-02-11 |
CA2318612A1 (en) | 2001-03-16 |
DE60041526D1 (en) | 2009-03-26 |
ATE422565T1 (en) | 2009-02-15 |
JP2001151571A (en) | 2001-06-05 |
ES2317825T3 (en) | 2009-05-01 |
FR2798654B1 (en) | 2001-10-19 |
FR2798654A1 (en) | 2001-03-23 |
EP1085109A1 (en) | 2001-03-21 |
CA2318612C (en) | 2011-07-12 |
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